Abstract
Blowout limits of cavity-stabilized flame of supercritical kerosene were experimentally studiedbyusing Mach 2.5 and 3.0 direct-connect supersonic model combustors operated under various air and fuel conditions. Specifically, the effects of the stagnation temperature and the stagnation pressure on the blowout limits were investigated for supercritical kerosene injected from the wall upstream of a cavity flameholder in a Mach 2.5 combustor. Experiments were performed under the same conditions for supercritical keroseneinjected from the rearpartofthe cavity bottomtostudy the influence of the location of fuel injection. The blowout limits of supercritical kerosene injected from the wall upstream of the cavity were further investigated in a Mach 3.0 combustor. Besides the effects of the stagnation temperature and stagnation pressure, the effect of the divergence angle of the combustor on the lean-fuel blowout limit was studied. Results show that there exist two blowout limits corresponding to the lean- and rich-fuel conditions for a given stagnation temperature. The location of fuel injection has substantial influence on the blowout limits, whereas the influenceof the stagnation pressure and the divergence angle of the combustor can be neglected in the range of interest.
| Original language | English |
|---|---|
| Pages (from-to) | 1161-1166 |
| Number of pages | 6 |
| Journal | Journal of Propulsion and Power |
| Volume | 30 |
| Issue number | 5 |
| DOIs | |
| Publication status | Published - 1 Sept 2014 |
ASJC Scopus subject areas
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science